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对翼型表面的结冰过程进行了准定常数值模拟。在每个时间步长内完成网格随着壁面边界的移动而更新、周围流场和水滴撞击特性重新计算、冰形计算及壁面边界的重构工作,如此循环直至所需的结冰计算时间。采用拉格朗日轨迹追踪法获得水滴撞击特性,应用考虑壁面粗糙度影响的边界层积分法计算壁面的对流换热系数,在此基础上求解Messinger结冰热力学模型,冰层始终沿壁面外法线方向生长。对NACA0012翼型在不同环境下生成的三种典型冰形进行了预测,并与实验结果进行了比较,表明本文所述方法的有效性。
The icing process of the airfoil surface is simulated by quasi constant values. In each time step, the grid is updated with the movement of the boundary of the wall, the recirculation of the flow field and the drop impact, the ice calculation and the reconstruction of the boundary of the wall are repeated until the required icing calculation time . The droplet impact characteristics were obtained by Lagrangian tracking method. The convective heat transfer coefficient of the wall surface was calculated by the boundary layer integral method considering the effect of the wall roughness. Based on this, the Messinger icing thermodynamic model was solved. The ice layer was always along the wall Line growth. Three typical ice formations of NACA0012 airfoil under different environments were predicted and compared with experimental results to show the effectiveness of the proposed method.